Time delay fuze for a rocket



July 17, 1956 K. L.. BAKER ETAI- TIME DELAY FUZE FOR A ROCKET 4Sheets-Sheet. 1

Filed Aug. 29, 1947 n NN July 17, 1956 K. L.BAK|:R ET A1- 2,754,759

TIME DELAY FUZE FOR A ROCKET Filed Aug. 29 1947 4 Sheets-Sheet 2 KLLBLZer A.AXeZs0l July 17, 1956 K. L. BAKER ET Al- TIME DELAY FUZE FOR AROCKET Filed Aug. 29, 1947 y .limuV/ Il? S/IOS |108 illl'll'l'll 4Sheets-Slime?l 3 Siwa/VMM KZ/.Baker CAAAxeZSon July 17, 1956 K. l..BAKER ET AL TIME DELAY FUZE FOR A ROCKET 4 Sheets-Sham, 4

Filed Aug. 29, 1947 United States Patent TIME DELAY FUZE Fon A ROCKETKennethl L. Bakerand Carl Axelson, Washington, ll). C;

Application August 29, 1947,- Serial No. 771,288 7 Claims. (Cl. 102;'71)

(Granted under Titia 35, Ui S. Code (1952), sec. 266) This` inventionrelates' generally to a time delay fuze for use with an armor piercingrocket and more particularly to a time delay fuze in which meanscontrolled by a predetermined amount of gas pressure produced as thepropellant charge of the rocket motor burns is adapted to arm the fuzeas' the rocket is propelled along the traject-'or' toward the target,the firing of the fnze being controlled by firing rineans rotatably andslideably arranged within the fuze casing and adapted to be rotated toan armed position and thereafter moved longitudinally to a tiringposition rin response to the sudden impact of 'the rocket with thetarget, at which time the tiring means are locked in the firingposition, whereupon the bursting charge within the rocket shell isdetonated in predetermined time delayed relation with respect to theaforesaid impact of the rocket with the target', such time' delay periodbeing controlled by a delay charge arranged within the' firing plungerslideably arranged within the ftize casing. Furthermore, on impact ofthe rocket with the target, the rocket is adapted to pierce the outerplates of a target such, for example',v as a naval vessel, aircraft, orthelike and to exp-lode the interior thereof whereby the force of theexplosion is concentrated on the vital interior structural arrangementof the' target.

More specifically the invention relates to' a fuze for a rocket in whichthe tiring means are maintained in a safe position during handling andtransportation and in which arm-ing thereof will not occur until afterthe rocket has been propelled from the launching rack and traveled apredetermined distance therefrom, the arming of the tuz'e' occurringduring the free iiight of the rocket toward the target.

One of the objects of the present invention is the provision of a' newand improved time dela-y fuze for a rocket inl which the tiring means ofthe fuze is locked in a safe position until the rocrcet is launched froma launching r'a'ck or tube', as the case may be, whereupon the tiringmeans is released from an initial locked safe position and rotated to anarmed position.

Anothery object of the present invention is the provision of a new andi'rriproved` time delay fuze for arocket in which a pressure controlledarming member is adapted to arm the fuze as the rocket is propelledtoward the target.

Another object of the present invention is the provision of anew andimproved fuze for a rocket inwhich arming means controlled by thepressure of combustion' of the propellant is releasably and rotatablysupported within the fuze' casing.` and adapted to rotate the firingmeans from' a safe position tio an armed position when the arming meanshave been released by the pressure controlled means.

A further object of the invention is the provision of a new and improvedfuze for a rocket having a rotatable armi-ng member arranged thereinadaptedy to be released and rotated to an armed position during the freeght of the rocket toward the target, and' in which the-tiring means issli'deabiy arranged therein and adapted to be locked in 2,754,759Patented July 17, 1956 the firing position upon impact of the rocketwith the target.

Still another object of the present invention is the provision of a new'and improved time delay fuze for a rocket in which the tiring meansthereof is adapted to be rotated from a safe position to an armedposition, and thereafter to be moved longitudinally to' a firingposition and det# nate the bursting charge within the rocket shell inpre# determined time delay relation with respect t the aforesaid impact.

Still other objects, advantages and improvements will be apparent fromthe following description, taken in connection with the accompanyingdrawings,- of which:

Fig; l is an elevational view of a rocket partially broken away andshowing the fuz'e' of th present invention scured thereto;

Fig.` 2 is an enlarged longitudinal sectional view of the fuze of Fig. 1and Showing the fuze in a safe or unarmed condition;

Fig. 3 is a transverse sectional view of the fuie taken on the line3"-'3 of Fig. 2;

Fig'. 4 is a transverse sectional view of the fiiz taken on the line'4-4 of Fig. 2;

Fig. 5 is a transverse sectional v'iew' of the fuze taken on the line'5=5 of Fig'. 2, and showing the means for preventing further movement ofthe arming member after the member has been rotated to an riiiedposition;

Fig'. 6 is a fragmentary elevational view of the ue partially brokenaway and in section and showing the' shear pin for' maintaining therotatable arming member in an' initial locked or safe position;

Fig. 7 is a View partially in longitudinal section and partially brokenaway showing the fuze in an armed con dition;

Figi. 8 is a transverse sectional view of the fuze taken on the line 8-Sof Fig. 7;

Fig. 9' is atransverse sectional View of the fuzev taken on the line9--9 of Fig. 7;

Fig. 10 is afrag'mentary longitudinal sectional view of the fuZe showingthe firing plunger in a iiing position;

Fig. l1 isa transverse sectional View ofthe fue taken 01'1 the line`11`11of Fig. l0 and showing, the arming meinberotated to the armedposition and a stop pin for preventing the further rotation thereof; and

Figl 12 is a transverse sectional View of they uz'e taken "ice l on theline IZ-12 of Figl. l() and showing a pair of detents for locking t-le'ringV plunger in the firing position.

Referring now to the drawings for a more complete understanding of theinvention and more particularly to Fig'. I thereof, there is shownthereon a rocket indicated generally by the reference character l0comprising a motor tube 11 having theusual rocket motor generallyindicated by the numeral 12 arranged' therein. Secured to' one end ofthemotor tube 11 in any suitable manner, preferably by thrfeadingthe partstogether, is a rocket head I3 comprisinga shell 14y having arrangedtherein a bursting charge 155. Disposed in one end of the headand'attached thereto as by an adapter 16 is the fuze of the presentinvention generally indicated by the referencei character 17.

rfhe rocket, Fig. 1, is a conventional type rocket and the motor thereofcomprises the usual component parts` such, for" eXample, as a propellant18, grid 19 for supporting the propellant within the tube 11, nozzle 21adapted' t'o direct' the gas jet in the desired direction as thevpropellant burns and to provide for expansion ofthe gases in`- the eXitcone ofthe nozzle, igniter 2v2, squib 23 arranged' in operativerelationwith respect to the ignit'er, andl conductors- 24 attached tothe squiband adapted to supply an electrical impulse thereto'Y as" the rocket is`launchedthereby to" fire' the" sq'uib and ignite theA igniter' which, inturn, ignites the propellant.

The motor tube 11 has secured to the other end thereof the usualstabilizing assembly generally indicated by the reference character 25comprising a plurality of ns 26, the ns being attached -to the -tube inany suitable mannei and extending radially therefrom and having a shroud27 'secured to the outer portions thereof. As lthe operation andstructure of the aforesaid rocket is wellknown to those skilled in theart, further detailed description of the operation and structuralarrangement thereof is deemed unnecessary as the aforesaid rocket isdisclosed for the purpose of more clearly illustrating the manner inwhich the fuze is armed in response to a predetermined amount ofpressure created by the propellant 18 as the propellant burns.

The adapter 16 is threaded into the open end of 'the head 13, Figs. l, 2and 3, and has a centrally disposed threaded bore 28 formed therein forthreaded engagement with the fuze 17, thus the fuze is secured to theadapter and extends a predetermined distance into the bursting charge15.

The fuze of the present invention comprises a casing I29 composed of anymaterial suitable for the purpose such, for example, as steel or thelike and is provided with a centrally disposed 'bore 31, in which is-arranged a plunger generally indicated by the numeral 32. The .plungercomprises a body 33 having trunnions 34 and 135 respectively formed onthe ends thereof which extend -outwardly therefrom and slidably androtatably support the plunger within the fuze casing 29. Arrangedwith-in a plurality of grooves 36 formed in the body 33 of the plungerare a plurality of anti-friction balls `37 adapted tto engage the walldelining the bore 31, thereby to permit the plunger to move slidably androtatably within 'the bore with no appreciable amount of frictionbetween lthe wall delning the bore and the plunger when the plunger isreleased. The balls are maintained within the grooves 36 by a washer 38and a collar 39 surrounding the trunnion 35 and secured to the body 33of the plunger .in any suitable manner such, for example, as by a pin41.

As shown on Figs. 2, 7 and 10 the plunger has formed `therein a bore orwell 42 having arranged therein a delay element generally indicated bythe numeral 43 and comprising a casing 44 within which is disposed adelay charge 45. One end portion of the delay charge is in proximatespace relation with respect -to one end of a detonator 46 arranged in areduced bore 47 and in communication with the bore 42 in the plunger,the other end of the detonator being in substantial abuttingengagementwith a 'lead-out charge 48 arranged in a transverse bore 49 disposedwithin the body 33 of the plunger. The lother end of the delay charge-is arranged in spaced 'relation with respect to a primer indicated bythe reference character 50 and adapted to re the del-ay charge by way ofbore 51 and passages 52 disposed within the ycasing 44.

The primer 50 is disposed within a well 53 formed in la nipple 54 andhaving threaded engagement with the threaded portion of bore 42, theprimer being clamped between the member 44 and nipple 54, Fig. 2.Threaded into the nipple 54 is a casing 55 having an explosive cap '56arranged -therein and adapted to be 'red as the rocket strikes thetarget. Arranged within a bore 57 formed in the nipple 54 is an annularmember 5'8 having a centrally disposed opening extending therethrough.Disposed in the opening and secured to the annular member '58 by a shearpin 60 is a firing piston 59 comprising a head `61 and a striker 62, thestriker being adapted to strike the primer 50 with suflicient force tocause tiring thereof when the cap 56 has been red upon impact of therocket wi-th the target. It will be understood, however, that when thecap 56 is tired, the force of the explosion therefrom will be sulhcientto sever the shear pin and drive the piston to'ward the primer 50 andthe striker 62 'thereon will strike the primer '50 with Sll- 4 cientforce to cause explosion thereof thus igniting the delay charge andtiring the detonator.

An anti-creep device 63 comprising a skirt 64 is arranged about aportion of the trunnion 35 and about an enlarged head 65 formed on thenipple 5'4, the anti-creep device being maintained on the trunnion andhead by a iange 66 formed thereon and clamped between the head 6'5 and aanged portion 67 formed on the casing 55. -As best shown on Fig. 2 theskirt 64 seals a pair of diametrically arranged ports 68 formed in thehead 65, the ports being in communication with lthe bore 57, the purposeof which will be more fully described hereinafter. Prematurelongitudinal movement of the plunger 32 after rotation thereof isprevented by a plurality of 5ta-bs 80 formed on the skirt 64 andextending outwardly therefrom and adapted to engage a disc 69. lUponirnpact these 'tabs are bent inwardly sufficiently to release theplunger for longitudinal movement.

The disc 69 has a centrally disposed opening 70 therein and is arrangedwithin an enlarged portion 71 of bore 31, the disc being maintainedwithin the aforesaid enlarged portion by a plug 72 having threadedengagement therewith. It will be understood, however, that when Itheplunger has been released and moved to a tiring position, Fig. 10, uponimpact of the rocket with a target, lthe plunger is forced toward atiring pin 73. The ring pin is secured to the plug 72 in any suitablemanner such, for example, as being pinned thereto and having a striker74 formed thereon adapted to extend into a recess T5 arranged in plug 72in such a manner as to have tiring engagement with the explosive cap 56when the plunger has been moved a predetermined amount in response toIthe aforesaid impact of the rocket with a target. As the plunger ismoved to the fir-ing position the anti-creep device attached thereto ismoved through opening 70 formed in disc 69 a predetermined amount andupon ring of the cap 56 in the aforesaid manner the skirt 64 of theanti-creep device is distorted or bulged as at 76 lat two pointsopposite ports 68, Fig. 10, -in response to the force of the explosionpartially directed thereagainst by way of the aforesaid bore 57 andports 68, it being understood, that the explosive force is also directedagainst the head 61 of the tiring piston 59, the divided force of theaforesaid explosion being controlled by a dellector 77 arranged in thebore 57. Thus the force of the explosion is suicient not only to causethe skirt 64 to be bulged in the aforesaid manner but also to drive thepiston 59 rearwardly with sucient force to cause the shear pin to besevered whereupon the striker 62 formed thereon will be driven intofiring engagement with the primer 50.

When the plunger has been moved longitudinally to the tiring position inresponse to the set-forward force as the rocket strikes the target, theskirt 64 will be bulged as heretofore described, the bulged portionsthereof being adapted to engage the disc 69 and prevent reverse movementof the plunger from the forward position thereof before it is locked bythe detent locking mechanism,

Fig. l0. When this occurs, a pair of diametrically disposed springcontrolled locking detents 78 slideably arranged within bores formed inthe casing are brought into axial alignment with their respective slots79 formed in the plunger 32, the detents being urged therein by a pairof springs 81 respectively arranged within Vthe aforesaid Figs. 7 and9,. the plunger 32 has been released and rofatedA from the safe positionto an armed position. With particular reference to Fig. 9 the detents 78remain` in engagement with the outer periphery of the plunger after theplunger has been rotated from the safe position to anr armed position, amovement of substantially 90, the slots 79 therein are thus brought intolongitudinal spaced alignment with respect to the detents 78 and uponimpact of the rocket with the target the plunger is drivenlongitudinally forwardly to the tiring position, Fig. l0, ard locked inthe firing position by the aforesaid detents 7 As shown on Figs. 2, 3,and 5 a pair of diametrically disposed pins 82 are secured to the casing2'9 in any suitable manner and extend into the bore 31 a predeterminedamount, the respective ends thereof having abutting engagement with theforward endrofV the plunger thus preventing longitudinal movement of theplunger within the bore 31 until the plunger has been rotatedsubstantially 90 by an arming memberY as will be hereafter more fullydescribed. It will be understood, however, that when the plunger hasbeen rotated substantially a quarter of a turn, the ends of the pins arebrought into spaced longitudinal alignment with a pair of complementarylongitudinall arranged slots 83 formed in the plunger thereby to permitfree passage of the plunger with respect to the pins as the plunger ismoved longitudinally within the bore 31 to the aforesaid tiringposition. It will be further understood, that when the plunger 32 isrotated substantially 90 the detents 78 are brought into spacedlongitudinal alignment with a pair of slots 79, such rotative movementalso being adapted to bring the slots 83 into spaced' longitudinalalignment with pins 82 thereby to permit longitudinal movement of theplunger to the ring position and also providing means for locking theplunger in the tiring position upon impact of the 'rocket with thetarget.`

As shown most clearly on Figs. 2 and 7 of the drawings there is arrangedwithin the casing 29 an arming device generally indicated by the numeral84 and comprising a bearing member 85 disposed within an enlarged recess86' formed in one end of the casing 29, the bearing member beingmaintained therein by an annular nut 87 having abutting engagement witha shoulder S8 formed on the bearing member 85 and adapted to be threadedinto the recess 86. Disposed within the bearing member 85 and rotatablysupported with respect thereto is a normally locked spring actuatedrotor 89 adapted to rotate the plunger 32 to an armed position whenreleased. The rotor is maintained within the bearing member by anannular disc 91 secured to the member in any suitable manner such, forexample, as by crimping one end portion of the member about the annulardisc Figs. 2, 6, 7 and 10.

The rotor 89 is rotatably supported by the disc 91 and a'. sleeve 92,releasably and slideably arranged within a bore 93 disposed in the rotor89 and an opening 94 in the member 85, the sleeve 92 being releasablysupported by a shear pin 95 extending through openings 96 in the sleeve92 and complementary openings 97 arranged in the bearing member.

A drive pin 98 extends through a slot 99 formed in trunnion 34A and intocorresponding openings 101 `arranged in the rotor 89, the pin alsoextending through a pair of slots 102 in sleeve 92. By this arrangement,a driving connection is provided between the plunger 32, arming member89 and sleeve 92 by pin 98 and rotative movement will be imparted tothese component parts when the shear pin 95 is severed, such rotationbeing imparted. thereto by a spring 103 surrounding the rotor 89 andhaving one end thereof anchored therein and the other end anchored inthe bearing 85. it will be understood', that when the shear pin 95 hasbeen severed the rotor', plunger, and sleeve will be rotated apredetermined amount such, for example, as approximately 90", the

rotation thereby being controlled by a stop pin 104 secured to thecasing 291m any suitable manner and extending through a recess 105 inthe bearing 8'5 and into a slot 106 formed in the rotor 89 Figs. 2, 5,and l1. A shoulder 107, Figs. 5 and ll, on the rotor and formed by thewall defining the slot 106 thereof is adapted to engage the pin 104 andprevent further rotation of the aforesaid' rotatable elements when theelements have been released and rotated substantially in response to theaction of spring 103.

When the plunger 32 has been rotated substantially 90 in the aforesaidmanner the lead-out charge 48 therein is brought into spacedlongitudinal alignment with respect to a pair of diametrically disposedbooster charges 108 arranged Within complementary recesses 109 formed incasing 29 as clearly shown on Fig. 7. A pair of additional diametricallydisposed boostercharges 111 are re` e' spectively arranged Withinrecesses 112 formed in the` casing 29 in proximate spaced relation withrespect to the charges 108 and adapted to be r'ed thereby. The aforesaidcharges 108 and 111 are maintained within their respective recesses by aretaining cup 113 enclosing the charges and having threaded engagementwith the casing 29.

As shown on Fig. l0 the plunger 32 has been moved to a firing positionin response to the impact of the rocket with a target and locked thereinby the aforesaid detents 78. When this occurs a. continuous tiring trainis provided from the cap 56 to the booster charges 108 by way of cap 56,primer 50, delay charge 45, detonator 46, lead-out charge 48 and boostercharges 108 and 111 which are adapted to tire the bursting charge 15.arranged within the shell 14 of the rocket head 13. It will beunderstood, however, that the bursting charge 15 will not be red by theaforesaid booster charges until a predetermined period of time haselapsed after the rocket strikes the target, the time delay period beingcontrolled by the delay charge 45 thus permitting' the rocket to piercethe outer structure or plates of the target and enter the interiorthereof before the bursting charge 15 is fired.

A plug generally indicated by the reference numeral 114 is threaded intoa well 115 formed in one end of the casingV 29 and comprises an end wall116 having a centrally disposed opening 117 arranged therein and anannular flange 118 formed thereon. Secured within the opening 117 as bythreaded engagement therewith is a valve 119 comprising a` casing 121having a centrally disposed bore 122 extending partially therethrough inwhich is arranged a. ball valve 123 adapted to normally seal arestricted bore 124, the bore being in communication with the bore 122.The ball valve 123 is urged in sealing engagement with respect to bore124 by a spring 125, one end thereof being in abutting engagement withthe ball valve, and the other end in engagement with a plug 126 securedin the casing 121 as by threaded engagement therewith.

A pair of diametrically disposed exhaust ports 127 are arranged withinthe casing 121 and in communication with the bore 122, the ports alsobeing in communication with a chamber 128 provided between the end wall116 on plug 114 and an end wall 129 formed on a cup-shaped member 131arranged within the well 115 and maintained therein by the aforesaidplug 114. Extending transversely through the casing 121 and incommunication with bore 124 is an inlet port 132,- thus providing meanswhereby the gas pressure created by the propellant 18 as the propellantburns is admitted therethrough and into chamber 12S when the pressurewithin the motor tube 12 has increased sufficiently to overcome thetension of the spring and unseat the valve 123.4

Clamped between a shoulder 133 formed within the well 115 and the member131 by the plug 114 is a flexible diaphragm 134 having a substantialportion thereof reinforced by a disc 135 secured thereto in any suitablemanner preferably as by soldering the parts together. It will beunderstood, however, that the diaphragm is adapted to be expanded inresponse to a predetermined amount of pressure exerted thereon, suchpressure being created in the aforesaid manner and entering into achamber 136 provided between the wall 129 and the diaphragm by way of anorifice 137 formed in the wall 129 and in communication with theaforesaid chambers 128 and 136. It will be further understood, that whena suicient amount of pressure has entered into chamber 136 by Way oforifice 137, the diaphragm will be forced into engagement with sleeve 92by the aforesaid pressure, whereupon the sleeve 92 is driven inwardly bythe expansion of the diaphragm suliiciently to cause the shear pin 95 tobe severed due to the frangibility thereof and the shearing actionexerted thereon as the sleeve 92 is moved inwardly with respect theretoin the aforesaid manner, the inward movement of the sleeve beingpermitted by the slots 83 formed there- Clamped between an enlarged head138 formed on the valve casing 121 and the end wall 116 of plug 114 is ascreen or filter member 139 adapted to permit the aforesaid gas pressureto enter into the chamber 128 by way of valve 119 but to exclude foreignmatter therefrom such, for example, as the particles of combustionproduced as the propellant 18 burns. The head 138 is also adapted toclamp a grip member 141 to the plug 114.

The aforesaid arming of the fuze will occur as the rocket is propelledalong the trajectory by the functioning of the motor 17 as is well knownto thoseskilled in the art, it being understood, however, that thepropellant charge of the rocket motor is ignited in the usual manner asthe rocket is launched from the launching rack or tube (not shown), asthe case may be. As the rocket is propelled along the trajectory by therocket motor a suiiicient amount of gas pressure enters into the chamber128 by way of valve 119 as the propellant charge burns and causesexpansion of the diaphragm 134, such expansion being sui'iicient todrive the sleeve 92 inwardly with sufficient force to cause the shearpin 95 to be severed.

When the shear pin has been severed, the arming member 89 is releasedand rotated substantially 90 to an armed position, Fig. 7, by the actionof spring 103, further rotation thereof being prevented by stop pin 104.It will be understood, however, that as the arming member is rotated,rotation of the plunger 32 is effected by the drive pin 98 secured tothe arming member and extending through slot 99 formed in trunnion 34 ofthe plunger. When this occurs, the lead-out charge 48 is brought intospaced longitudinal alignment with the booster charges 108, Fig. 7, andthe slots 83 are brought into spaced longitudinal alignment with pins 82thus permitting free longitudinal movement of the plunger to a tiringposition upon impact of the rocket with the target, the pins 82preventing longitudinal movement of the plunger until the plunger hasbeen moved to an armed position in the aforesaid manner. As the rocketstrikes the target the plunger ismoved to the tiring position inresponse to the set-forward force applied thereto, whereupon theexplosive cap 56 is fired by the tiring pin 73, the force of theexplosion being suiicient to cause the skirt 64 to be bulged as at 76and hold the plunger momentarily, thereby to permit the locking detents78 to be urged into their respective slots 79, thus locking the plungerin the firing position. As the cap 56 is tired by the firing pin 73, theforce of the explosion is suicient not only to bulge the skirt 64 butalso to sever the shear pin 60 and drive the piston toward primer 50,whereupon the striker 62 thereon will strike theY primer with sufficientforce to cause explosion thereof, the fiash therefrom igniting the delaycharge 45 thereby exploding the detonator 46 when a predetermined periodof time has elapsed. The detonator fires the leadout charge 48 andthebooster charges 108 are red thereby ,whichinitiates firing of theauxiliary booster charges 111 and concurrently therewith theburstingvcharge 15 is tired and fragmentation of the shell occurs.

Briefly stated in summary, the -present invention cornprises theprovision of a new and improved Vtime delay fuze for an armor piercingrocket in which -means are provided for tiring an explosive chargearranged within the rocket shell in predetermined time delayed relationwith respect to impact of the rocket with the target, and in which thearming means is controlled by gas pressure formed by combustion of therocket propellant and adapted to release a rotor within the fuze as therocket is propelled along the trajectory thereby to rotate a firingplunger from an initial safe position to an armed position, the plungerthereafter being adapted to be moved longitudinally to a firing positionand locked therein as the,

rocket strikes the target, and in which means are provided fordetonating the bursting charge arranged within the rocket shell when apredetermined period of time has elapsed after impact of the rocket withthe target.

While the invention has been described with reference to a preferredVexample Vthereof which gives satisfactory results, it will be obviousto those skilled in the art to which the invention pertains, afterunderstanding the in-` vention, that various changes and modificationsmay be made Without departing from the spirit and scope of theinvention, and it is intended therefore, in the appended claims, tocover all such changes and modifications.

The invention herein described and claimed may be manufactured and usedby or for the Government of the United States of America forgovernmental purposes without payment of any royalties thereon ortherefor.

What is claimed as new and desired to be secured by Letters Patent ofthe United States is:

l. A time delay fuze for a rocket comprising a casing, a pair of boostercharges arranged within said casing, an arming member releasably androtatably supported within said casing in a safe position and adapted tobe ro-l tated to an armed position when released, means including adevice slideably arranged within said arming member and releasablysecured to the casing for maintaining the arming member in said safeposition, means secured to the casing and the arming member for rotatingthe arming member a predetermined amount to said armed position when thearming member is released, flexible means sealed to the casing andnormally spaced from said device for moving said device suiciently torelease the device from the casing as the flexible means is moved intoengagement with the device in response to the pressure applied to theflexible means as the rocket travels along a trajectory, a firingplunger rotatably supported within the casing and adapted to be rotatedto an armed position and moved longitudinally to a firing position uponimpact of the rocket with a target, a bifurcated portion on saidplunger, driving means on said arming member and slideably disposedwithin said bifurcated portion for rotating the plunger to said armedposition thereof when the arming member is rotated said predeterminedamount, explosure means including a time delay element arranged withinsaid plunger for tiring said booster charges when a predetermined periodof time has elapsed after said irnpact, and means on the casing forfiring said explosive means upon forcible engagement therewith as theplunger moves to said tiring position in response to said impact.

2. A time delay fuze for a rocket comprising a casing having a pair ofdiametrically disposed recesses formed therein, a pair of boostercharges respectively arranged within said recesses, an arming memberreleasably and rotatably supported within said casing in an initial safeposition and adapted to be rotated to an armed position when released,means including a shearable member secured to said casing andoperatively connected to said arming member for maintaining the armingmember in said initial safe position and adapted to release the armingmember when severed in response to a predetermined pressure appliedthereto, pressure controlled means sealed to the casing and movable intoengagement with said arming member by pressure applied thereto from thecombustion of thel rocket propellant as the rocket travels along atrajectory for applying said pressure tothe shearable member, springmeans secured to the casing and arming member for rotating the armingmember to said armed position as said shearable member is severed,spring urged valve means on the casing in communication with saidpropellant and said pressure controlled means for applying said pressureto the pressure controlled means when the pressure from said propellanthas reached a predetermined value, a tiring plunger rotatably supportedwithin the casing and adapted to be rotated to an armed position by saidarming member and moved longitudinally to a tiring position upon impactof the rocket with a target, a bifurcated portion on said plunger, drivemeans on the arming member and disposed within said bifurcated portionfor rotating the plunger to said armed position as the arming member isreleased, explosive means including a time delay element arranged withinsaid plunger for ring said booster charges when a predetermined periodof time has elapsed after said impact, means on the casing for tiringsaid explosive means when thel plunger is moved to said armed. positionand the explosive charge is driven into tiring engagement therewith inresponse to said impact, a plurality of yieldable tabs carried by saidplunger and extending outwardly therefrom, and means on said casing inthe path of travel of said tabs for preventing said longitudinalmovement of the plunger until said impact.

3. A time delay fuze for a rocket comprising a casing, a pair of boostercharges arranged within said casing, an arming member releasably androtatably supported within said casing in an initial safe position, asleeve disposed within said arming member and slideably arranged withinsaid casing for supporting the arming member Within the casing,shearable locking means secured to the casing and sleeve for releasingthe arming member for rotation to said armed position when the lockingmeans is severed in response to a predetermined amount of movement ofsaid sleeve, spring means secured to the casing and arming member forrotating the arming member to said armed position as the arming memberis released, a firing plunger rotatably supported within the casing andadapted to be rotated to an armed position by said arming member andmoved longitudinally to a firing position upon impact of the rocket witha target, said plunger having a slot formed therein, a drive pin securedto the arming member and slideably disposed within said slot formed insaid plunger for rotating the plunger to said armed position in responseto rotation of the arming member, explosive means carried by saidplunger and including a time delay element for ring said booster chargewhen a predetermined period of time has elapsed after the explosivemeans is tired, means on the casing for ring said explosive means uponforcible engagement therewith when the plunger is moved to said firingposition, a plurality of yieldable elements carried by and extendingoutwardly from the plunger, and means on said casing in the path oftravel of said elements for preventing said longitudinal movement of theplunger to said firing position until said impact.

4. A time delay fuze for a rocket comprising a casing, a pair of boostercharges arranged within said casing, a normally locked tiring plungerreleasably and rotatably arranged within the casing and adapted to berotated from an initial safe position to an armed position when releasedand to be moved to a tiring position in response to said impact, saidplunger having a slot formed therein, a shear pin secured to said casingand disposed Within said slot for locking the plunger against rotationto said armed position until said pin is severed in response to apredetermined amount of pressure applied thereto, an arming memberrotatably supported within the casing and locked against rotation bysaid shear pin and adapted to be rotated a predetermined amount whensaid shear pin is severed, sleeve means releasably supported within thearming member by said shear pin for severing the pin in response to saidpressure thereon as the sleeve is moved a predetermined amount, a exiblediaphragm sealed to the casing andy movable into engagement with saidsleeve by the gas pressure of combustion of the rocket propellant formoving the sleeve said predetermined amount,- means on said armingmember and secured to the casing for rotating the arming member saidpredetermined amount, means secured to the arming member and traversingsaid slot for rotating the plunger from said initial safe position tosaid armed position when the arming member is released and rotated saidpredetermined amount, means including a time delay element arrangedWithin the plunger for tiring said booster charge in time delayedrelation with respect to said impact, and means on the casing for firingsaid last named means upon forcible engagement therewith as the plungeris moved to said tiring position in response to said impact.

5. A fuze for a rocket comprising a casing, a normally locked firingplunger releasably and rotatably arranged' within the casing and adaptedto be rotated from an initial safe position to an armed position whenreleased and to be moved to a tiring position upon impact of the rocketwith a target, a bifurcatedportion on said plunger, shearable lockingmeans secured to saidV casing and traversing said bifurcated portion forlocking the plunger against rotationl to said armed position until the.shearable means is` severed in response to a predetermined amount ofpressure applied thereto, sleeve means releasably supported within. thecasing by said shearable locking means for applying said pressurethereto, means sealed to the casing and movable into engagement withsaid sleeve means by gas pressure from combustion of the rocketpropellant for applying said pressure to the sleeve means, arming meansrotatably supported within the casing and connected for rotation withthe plunger and adapted to be rotated a predetermined amount when saidlocking means is severed, means on said arming means and secured to thecasing for rotating the arming means said predetermined amount, meanssecured to the arming means and traversing said bifurcated portion forrotating the plunger from said initial safe position to said armedposition when the plunger is released and the arming means is rotatedsaid predetermined amount, explosive means carried by said plunger, andmeans on the casing and normally spaced from said plunger for tiringsaid explosive means upon forcible engagement therewith when the plungeris moved to said firing position in response to said impact.

6. A time delay fuze for a rocket comprising a casing, a pair of boostercharges arranged Within said casing, rotor means releasably supportedwithin said casing and adapted to be rotated a predetermined amount whenthe rotor means is released, spring means on said rotor means andsecured to the casing for rotating the rotor means said predeterminedamount as the rotor means is released, a shear pin secured to the casingand operatively connected to said rotor means for releasably supportingthe rotor means within the casing and adapted to prevent rotationthereof until said shear pin is severed, means including a flexiblediaphragm sealed within the casing and movable by gas pressure ofcombustion of the rocket propellant for causing the shear pin to besevered as said diaphragm is forcibly driven into engagement with therotor means in response to an increase in said pressure, a plungeroperatively connected to the rotor means for rotation from an initialsafe position to an armed position as the rotor means is rotated saidpredetermined amount, said plunger being adapted to be movedlongitudinally to a tiring position upon impact of the rocket with atarget, a bifurcated portion on said plunger, means on the rotor meansand disposed within said bifurcated portion for rotating the plungerfrom said initial safe position to said armed position as the rotormeans is released and rotated said predetermined amount, yieldable meanson the plunger in engagement with the casing for releasably locking theplunger in said armed position until said impact, explosive meansincluding a time delay element arranged with the plunger for tiring saidbooster chargesin timedelayed relation with respect to said impact, andmeans on said casing for ring said explosive means upon forcible en-vgagement therewith when ythe plunger is lreleased and driven into saidtiring position in response to said impact-` 7.l A time delay fuze for arocket comprising a casing, a pair of booster charges arranged withinsaid casing, a plunger rotatably and slideably supported within thecas-v ing in an initial safe position and adapted to be rotated to anarmed position as the rocket travels along a trajectory, said plungerbeing adapted to be moved slideably from said armed position to a firingposition in response to impact of the rocket with a target, a pair ofstop pins secured to said casing, complementary means on the plunger inengagement with said stop pins for preventing said sliding movement ofthe plunger until the plunger has been rotated to said armed positon,rotatable arming means releasably secured to said casing and rotativelyconnected to the plunger and adapted to be rotated a predeterminedamount when released, a bifurcated portion on said plunger, a shear pinsecured to the casing and disposed within said bifurcated portion forreleasing the arming means and plunger when the pin is severed inresponse to a predetermined pressure applied thereto, a

flexible diaphragm sealed within the casing and movable 25 intoengagement with said arming means by gas pressure of combustion of therocket propellant thereon for apply ing said pressure to the shear pin,drive means on said l2 arming means and rotatable therewith anddisposed' slide-f ably within said bifurcatedV portion for rotating saidplunger fromY said initial safe position to said armed position when thearming means is released and rotated said predetermined amount,explosive means including a time delay element carried by the plungerfor firing said booster charges in predetermined time delayed relationwith respect to said impact, means on said casing and forciblyengageable with said explosive means to cause tiring thereof as theplunger is driven to said ring position, means' on said plunger andeffective by the force of the explosion as the explosive means is redfor momentarily maintaining the plunger in said tiring position, a pairof detents on the casing, and complementary means on the l plunger andadapted to coact with said detents for locking the plunger in saidfiring position.

References Cited in the le oi' this patent UNITED STATES PATENTS YWoodberry May 3, 1921 2,145,507 Denoix Jan. 31, 1939 2,397,781 FischerApr. 2, 1946 2,409,205 Graumann Oct. 15, 1946 2,441,897 Nichols May 18,1948 FOREIGN PATENTS 257,335 Great Britain Aug` 27, 1926 wad.; 't i

